高超声速气动热标模HyHERM-Ⅰ试验

doi:10.7527/S1000-6893.2022.27804

Abstract

Abstract:

The ground test study on hypersonic aero-heating standard model has been carried out， so as to meet the needs of the development of hypersonic aero-heating environment prediction and evaluation. The test covers different Mach number （6， 8， 10， 12）， Reynolds number， total temperature， leading edge radius， and angle of attack. The uncertainty of flow field parameters is analyzed in detail. The uncertainty of Ma， Re， T₀ and P₀ is better than ±1%， ±10%， ±6%， ±3% respectively. A "plate-double wedge" test model HyHERM-I is designed， which characterize the two-dimensional hypersonic flow. The heat flux and boundary layer flow state is measured by thin film gauge or thermocouple， and the flow characteristics of the separation zone are analyzed with high-speed schlieren. The test results show that， the repeatability measurement accuracy of stagnation-point heat flux is better than ±5%. Smaller leading edge radius and larger compression angle results in a larger separation zone. The boundary layer flow is more likely to transition and develop into turbulence while smaller leading edge radius， larger Reynolds number， low Mach number. Besides， the flow separation is restrained by the transition and turbulence flow. The test data of HyHERM-I can be used as a reference for numerical verification and validation， testing technology validation， correlation study between flight and ground test， as well as for hypersonic vehicle design.

Key words: Hypersonic aero-Heating Environment Research Model (HyHERM), shock tunnel, heat flux, boundary-layer, flow separation

CLC Number:

V211

Shouchao HU, Yu ZHUANG, Xian LI, Tao JIANG. Hypersonic aero-heating environment research model HyHERM-I: Experiment[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 233-248.

Figures/Tables 20

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位置	编号	流向X/mm	法向Y/mm	展向Z/mm	测点数
前缘线	1	-217/-242	0	-120	1
	2	-217/-242	0	-80	1
	3	-217/-242	0	-40	1
	4	-217/-242	0	0	1
	5	-217/-242	0	40	1
	6	-217/-242	0	80	1
	7	-217/-242	0	120	1
平板	1	-190	×2	0	2
	2	-140	×2	0	2
	3	-90	×2	0	2
	4	-40	×2	0/±60	6
	5	-30	×2	0	2
	6	-20	×2	0	2
	7	-10	×2	0	2
	8	-6	×2	0	2
楔	9	6	×2	0/±60	6
	10	10	×2	0	2
	11	20	×2	0	2
	12	30	×2	0	2
	13	40	×2	0/±60	6
	14	60	×2	0	2
	15	80	×2	0	2
	16	100	×2	0	2
	17	120	×2	0	2
合计					53

参数		流场						偏差（不确定度）/%
参数		1	2	3	4	5	6	偏差（不确定度）/%
总温T₀/K		640	1 540	1 540	940	930	1 540	±6
总压P₀/MPa		2.14	7.37	11.12	3.85	22.59	17.17	±3
马赫数Ma		5.7	8.0	10.1	10.0	10.4	12.1	±1
单位雷诺数Re/m^-1		1.3×10⁷	4.0×10⁶	3.2×10⁶	3.1×10⁶	1.7×10⁷	3.1×10⁶	±10
静温T/K		86	121	78	46	42	55
静压P/Pa		1 841	659	214	88	397	98
密度ρ/（kg·m^-3）		7.20×10^-2	1.84×10^-2	9.24×10^-3	6.40×10^-3	3.16×10^-2	6.00×10^-3
自由流速度U/（m·s^-1）		1 079	1 792	1 817	1 385	1 379	1 830
驻点热流测量值/（W·cm^-2）		26.43	97.32	62.13	20.46	43.98	51.39	±5
F-R_Newton	计算值/（W·cm^-2）	25.27	88.74	63.83	19.16	41.64	51.75
F-R_Newton	与试验值偏差/%	4.39	8.82	-2.74	6.35	5.32	-0.70
F-R_Stokes	计算值/（W·cm^-2）	28.15	99.93	72.03	21.52	46.77	58.47
F-R_Stokes	与试验值偏差/%	-6.51	-2.68	-15.93	-5.18	-6.34	-13.78

序号	流场	攻角α/（º）	前缘半径R/mm	等效组合
1	1	0	5	Ⅱ Ⅲ
2	1	-15		Ⅳ Ⅰ
3	2	0		Ⅱ Ⅲ
4	2	-15		Ⅳ Ⅰ
5	3	0		Ⅱ Ⅲ
6	3	-15		Ⅳ Ⅰ
7	4	0		Ⅱ Ⅲ
8	4	-15		Ⅳ Ⅰ
9	5	0		Ⅱ Ⅲ
10	5	-15		Ⅳ Ⅰ
11	6	0		Ⅱ Ⅲ
12	6	-15		Ⅳ Ⅰ
13	3	0	1	Ⅱ Ⅲ
14	4	0		Ⅱ Ⅲ
15	5	0		Ⅱ Ⅲ

试验状态		分离点距拐角长度L_s/mm	再附点距拐角长度L_r/mm	分离激波角β_ss/（°）	主激波角β_ms/（°）
1	上表面	46	17	21.5	9.0
1	下表面	25	10	11.5	13.4
2	上表面	78	58	20.1
2	下表面	24	11	20.0	13.6
3	上表面	75	29	18.6	8.0
3	下表面	27	16	17.6	8.4
4	上表面	115	66	17.0
4	下表面	32	14	20.0	12.7
5	上表面	64	32	20.1	6.3
5	下表面	42	25	16.9	7.2
6	上表面	135	61	14.0
6	下表面	32	25	19.7
7	上表面	81	39	17.9	6.4
7	下表面	71	28	16.7	7.0
8	上表面	151	69	11.1
8	下表面	50	33	19.7
9	上表面	61	23	18.3	7.7
9	下表面	38	16	11.3	3.4
10	上表面	145	66	15.4
10	下表面	25	17	19.2	11.0
11	上表面	80	46	19.0	7.3
11	下表面	40	27	15.3	4.7
12	上表面	133	85	12.2
12	下表面	42	26	20.0
13	上表面	179	66	13.3
13	下表面	46	17	16.7	7.2
14	上表面	180	70	13.5
14	下表面	56	28	12.3	6.7
15	上表面	152	63	11.0
15	下表面	58	24	14.3	8.5

流场	半径R/mm	攻角α/（°）	流场前缘热流值/（W·cm^-2）							测量平均值/（W·cm^-2）	F-R_Newton		F-R_Stokes
流场	半径R/mm	攻角α/（°）	1	2	3	4	5	6	7	测量平均值/（W·cm^-2）	计算值/（W·cm^-2）	偏差/%	计算值/（W·cm^-2）	偏差/%
1	5	0	34.16	34.42	35.14	35.88	36.76	34.98	35.72	35.29	30.95	12	34.48	2
1		-15	34.06	36.19	34.07	38.30	36.71	36.52	33.32	35.60
2		0	125.46	118.06	120.47	121.02	119.29	125.24	120.65	121.46	108.68	11	122.39	-1
2		-15	124.38	115.77	116.75	121.04	114.58	124.23	123.38	120.02
3		0	74.25	72.10	73.14	74.11	74.66	76.45	74.23	74.13	78.18	-5	88.22	-19
3		-15	70.52	67.59	70.22	70.95	69.51	71.31	70.80	70.13
4		0	26.37	25.39	25.58	26.49	25.95	27.08	25.69	26.08	23.47	10	26.36	-1
4		-15	25.72	24.74	25.51	25.61	25.02	25.65	24.83	25.30
5		0	54.26	53.82	54.83	54.64	53.18	54.86	54.13	54.25	51.00	6	57.28	-6
5		-15	51.63	50.11	49.96	50.70	50.54	50.00	50.49	50.49
6		0	62.83	62.96	63.35	63.17	64.85	63.68	63.01	63.41	63.38	0	71.61	-13
6		-15	61.59	60.76	61.42	62.01	60.92	62.75	61.39	61.55
3	1	0	183.48	180.01	193.62	181.00	192.32	186.27		186.12	174.81	6	197.26	-6
4		0	62.85	59.13	69.34	69.10	69.10	64.21		65.62	52.47	20	58.93	10
5		0	130.65	127.90	141.69	144.47	145.50	133.89		137.35	114.04	17	128.08	7

Hypersonic aero-heating environment research model HyHERM-I: Experiment

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